GB1201526A - Gas turbine power units - Google Patents
Gas turbine power unitsInfo
- Publication number
- GB1201526A GB1201526A GB2513568A GB2513568A GB1201526A GB 1201526 A GB1201526 A GB 1201526A GB 2513568 A GB2513568 A GB 2513568A GB 2513568 A GB2513568 A GB 2513568A GB 1201526 A GB1201526 A GB 1201526A
- Authority
- GB
- United Kingdom
- Prior art keywords
- turbine
- compressor
- duct
- propulsion
- combustion chamber
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
- F02K3/12—Plants including a gas turbine driving a compressor or a ducted fan characterised by having more than one gas turbine
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
Abstract
1,201,526. Jet propulsion plant; gas turbine combustion chambers. G.H. GARRAWAY. May 25, 1968 No.25135/68. Heading F1J and F1L. An aircraft propulsion unit comprises a gas turbine jet propulsion engine formed by a compressor 10, turbine 12 and propulsion nozzle 31, and a lift fan or propellor 22 connected to a turbine 20 which can be driven by the products from a combustion chamber 25 connected to compressor 10 by a duct 19. Duct 19a may supply a further fan or propeller driving turbine. Some of the air leaving compressor 10 is always supplied to a duct 14 where it is burnt with fuel from burners 15 to drive turbine 12. The remaining portion of air leaving the compressor enters a manifold 16 from which it is selectively supplied according to the setting of valves 17, 18, 18a to ducts 19 and/ or 26, 26a. The latter ducts connect with a further combustion chamber 27 in which fuel and air may be burnt in stoichiometric proportions before expanding through a propulsion nozzle 30. Thus, according to the requirements of the aircraft in which the unit is mounted, the propulsion nozzle 30 and the propeller or lift fan 22 can be operated individually or together. Valves 17, 18 can be controlled manually by the pilot or automatically in response to variables such as engine speed or aircraft speed or altitude. Nozzle 31 receives the exhaust gases of turbine 12 under all operating conditions and the thrust thereof may be increased by reheat fuel injected at 32. The exhaust gases cool the surface of combustion chamber 27 when the latter is operating. The exhaust gases of turbine 20 pass to an additional propulsion nozzle 24. Attitude control of the aircraft during lift fan take-off operation can be effected by a propulsion unit 50 receiving fuel through an inlet 53 and air from the compressor 10 via a duct 51 and valve 52. In a modification, Fig.2, combustion chamber 27 is replaced by a combustion chamber 270 remote from the exhaust of turbine 12 and supplied with air from compressor 10 for stoichiometric combustion via a duct 260.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2513568A GB1201526A (en) | 1968-05-25 | 1968-05-25 | Gas turbine power units |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| GB2513568A GB1201526A (en) | 1968-05-25 | 1968-05-25 | Gas turbine power units |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1201526A true GB1201526A (en) | 1970-08-05 |
Family
ID=10222780
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB2513568A Expired GB1201526A (en) | 1968-05-25 | 1968-05-25 | Gas turbine power units |
Country Status (1)
| Country | Link |
|---|---|
| GB (1) | GB1201526A (en) |
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1331386A2 (en) * | 2002-01-16 | 2003-07-30 | National Aerospace Laboratory of Japan | Multi-turbofan system with separate core engine |
| RU2443480C1 (en) * | 2009-06-26 | 2012-02-27 | Гэз Тербайн Иффишенси Свиден Аб | Spraying system, system to increase engine power output with spraying system, and method of air humidification |
| RU2562822C2 (en) * | 2014-01-09 | 2015-09-10 | Общество с ограниченной ответственностью "Спектралазер" | Aircraft gas turbine engine and method of its speedup |
| RU2623588C2 (en) * | 2015-01-27 | 2017-06-28 | Виктор Серафимович Бахирев | Turbojet |
| RU2644721C2 (en) * | 2016-06-23 | 2018-02-13 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Aircraft power plant |
| RU2791783C1 (en) * | 2021-12-10 | 2023-03-13 | Анатолий Михайлович Криштоп | Krishtop combined turboprop - turbojet engine (ktvtrdk) and method of its functioning |
-
1968
- 1968-05-25 GB GB2513568A patent/GB1201526A/en not_active Expired
Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1331386A2 (en) * | 2002-01-16 | 2003-07-30 | National Aerospace Laboratory of Japan | Multi-turbofan system with separate core engine |
| EP1331386A3 (en) * | 2002-01-16 | 2005-01-05 | National Aerospace Laboratory of Japan | Multi-turbofan system with separate core engine |
| RU2443480C1 (en) * | 2009-06-26 | 2012-02-27 | Гэз Тербайн Иффишенси Свиден Аб | Spraying system, system to increase engine power output with spraying system, and method of air humidification |
| RU2562822C2 (en) * | 2014-01-09 | 2015-09-10 | Общество с ограниченной ответственностью "Спектралазер" | Aircraft gas turbine engine and method of its speedup |
| RU2623588C2 (en) * | 2015-01-27 | 2017-06-28 | Виктор Серафимович Бахирев | Turbojet |
| RU2644721C2 (en) * | 2016-06-23 | 2018-02-13 | Федеральное государственное унитарное предприятие "Центральный институт авиационного моторостроения имени П.И. Баранова" | Aircraft power plant |
| RU2791783C1 (en) * | 2021-12-10 | 2023-03-13 | Анатолий Михайлович Криштоп | Krishtop combined turboprop - turbojet engine (ktvtrdk) and method of its functioning |
| RU2815564C1 (en) * | 2023-03-11 | 2024-03-18 | Федеральное государственное бюджетное образовательное учреждение высшего образования "Казанский национальный исследовательский технический университет им. А.Н. Туполева - КАИ" | Aircraft power plant |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed | ||
| PLNP | Patent lapsed through nonpayment of renewal fees |